某发动机并联贮箱排放均衡性研究  

Research on equalizing discharge of parallel tank for a liquid rocket engine

作　　者：李纯飞[1] 龙春伟 董苑[1] LI Chunfei;LONG Chunwei;DONG Yuan(Xi＇an Aerospace Propulsion Institute, Xi＇an 710100, China)

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2018年第3期76-80,86,共6页Journal of Rocket Propulsion

基　　金：国家863项目(2015AA7060210)

摘　　要：某发动机系统采用两台并联布局的贮箱供应推进剂,推进剂排放存在不均衡,其排放均衡性与发动机管路流阻特性、推力装置工作特性、发动机结构布局有关。为获得影响该发动机系统排放均衡性的主导因素,并为改善系统排放均衡性提供依据,建立了分析模型,搭建了试验系统,计算分析与试验验证了上述因素影响情况。计算及试验结果表明,发动机管路流阻特性、发动机结构布局为主导因素,对系统排放均衡性影响较大,推力装置工作特性影响很小。据此,提出了可行的改进措施,包括控制发动机管路流阻特性和优化发动机结构布局。Two parallel tanks are arranged to supply propellant simultaneously in a liquid rocket engine,but the propellant discharge is not balanced. It is associated with the flow resistance of the engine pipeline,the thruster working performance and the structural layout of the engine. In order to obtain the dominate factors affecting the discharge balance of the engine system and provide the measure for eliminating the unequal discharge of the parallel tank,an analysis model and a testing system were established to verify the influence of these above factors through the computational analysis and test. The results show that the pipeline flow resistance and the structural layout of the engine are the main factors,while the influence of the thruster working performance is very small. Accordingly,the feasible improvement measures are achieved to control the pipeline flow resistance and optimize the structural layout of the engine.

关 键 词：液体发动机 均衡排放 并联贮箱 分析模型 改进措施 

分 类 号：V433-34[航空宇航科学与技术—航空宇航推进理论与工程]